A system and method for improved system efficiency of an integrated power and control unit (IPCU) of an aircraft is disclosed. The system uses an open-loop cooling system and turbo machine power matching to provide wide operation range without over-sizing. In order to reduce the temperature of the air flow through the cooling heat exchanger, the cooling turbine need to expand further in the same time generating power but the power could be higher than the compressor could absorb so a generator that would convert the power and used in supplying the aircraft would result in more efficient system.

A method for manufacturing a compressor impeller wherein the compressor impeller is cast using a mold. As a first alternative, the mold is made using 3D printing. As a second alternative, a model of the compressor impeller is made using 3D printing, and the mold is then made on the basis of said model.

A pump arrangement includes an axial-flow machine and a drive to convey fluid mounted in a housing. The axial-flow machine is formed by at least one first rotor having permanent magnets, a shaft connected to the first rotor and a stator arrangement with stator teeth distributed concentrically around the shaft axis circumferentially and axially separated from the first rotor by an air gap. The stator teeth have axially-opposite end portions and a tooth core therebetween wound with at least one coil winding. The second end portion, turned away from the first rotor, of each stator tooth forms a tooth root joined to a back plate. The first rotor is an eccentric disk and on the side away from the stator arrangement has an eccentric cam, radially spaced from the shaft axis, and rotatably and torque-transmittingly connected to the drive. An axial-flow machine and a compressor includes the pump arrangement.

A propulsor for a gas turbine engine includes, among other things, a case including a duct disposed along an axis to define a flow path. A rotor includes a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path. A row of guide vanes are situated in the flow path. At least two of the guide vanes extend in the generally radial direction between inner and outer surfaces of the duct, extends in a chordwise direction between a first leading edge and a first trailing edge to define a vane chord dimension (VCD) at a first span position of the corresponding guide vane, and defines a vane circumferential pitch (VCP) at the first span position of the corresponding guide vane and an adjacent one of the guide vanes. The row of guide vanes has a vane solidity (VR) defined as VCD/VCP, the vane solidity (VR) being equal to or less than 1.43.

An abrasive tip comprises an additive layer having an additive; the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.

A modeling method for a fan assembly includes constructing non-axially symmetric end wall curved surfaces in a cascade channel. Constructing the non-axially symmetric end wall curved surfaces in the cascade channel includes: determining, using a flow path design method for a dual flow path of a blade end area, an initial axially symmetric curve radius and a recessed curve lowest point radius of non-axially symmetric curved surfaces; and constructing the non-axially symmetric end wall curved surfaces in the cascade channel according to the initial axially symmetric curve radius and the recessed curve lowest point radius. The modeling method constructs the non-axially symmetric end wall curved surfaces in the cascade channel using the flow path design method for a dual flow path of a blade end area, to implement the control of flow directions by the non-axially symmetric curved surfaces, thereby reducing end wall loss.

A fluid processor for use in a downhole pumping operation includes a fluid processing stag, a nozzle stage and a gas compressor stage. The nozzle chamber is configured as a convergent-divergent nozzle and the variable metering member is configured for axial displacement within the convergent section to adjust the open cross-sectional area of the nozzle. A method for producing fluid hydrocarbons from a subterranean wellbore with a pumping system includes the steps of measuring a first gas-to-liquid ratio of the fluid hydrocarbons and operating a motor within the pumping system to operate at a first rotational speed. The method continues with the steps of measuring a second gas-to-liquid ration of the fluid hydrocarbons with the sensor module, where the second gas-to-liquid ratio is greater than the first gas-to-liquid ratio, and operating the motor at a second rotational speed that is faster than the first rotational speed.

A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.

A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.